高分多模卫星高刚度太阳翼机构设计与验证  

Mechanical Design and Verification of GFDM-1 Satellite High-stiffness Solar Arrays

作　　者：商红军[1] 任守志[1] 盛聪[1] 郑树杰 SHANG Hongjun;REN Shouzhi;SHENG Cong;ZHENG Shujie(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Beijing Spacecrafts,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]北京卫星制造厂有限公司,北京100094

出　　处：《航天器工程》2021年第3期156-163,共8页Spacecraft Engineering

基　　金：国家重大科技专项工程。

摘　　要：针对传统多板串联一维展开的刚性太阳翼无法实现展开状态高刚度和低惯量的问题,提出了一种三板并联二维展开的高刚度太阳翼机构方案,通过采用构型优化、高刚度基板设计和高刚度铰链等设计技术和方法,实现了刚性太阳翼的高刚度、低惯量要求,为高分多模卫星配套研制了两套三板并联、低惯量、高刚度太阳翼。经过高分多模卫星太阳翼地面试验及在轨飞行验证,结果表明:与相同面积的传统串联太阳翼相比,三板并联二维展开太阳翼的展开状态刚度提高5倍以上,转动惯量减小至1/8,该技术可为后续高刚度太阳翼机构设计及研制提供参考。High resolution remote satellites unsurely need high deployed stiffness and low deployed inertia rigid solar array,but the traditional multi-panel in-line rigid solar array widely used for spacecraft can’t meet these requirements.In terms of this problem,a three-panel in-parallel 2D deployment rigid solar array mechanism concept is developed in this paper.New designs and technologies such as configuration optimum,high stiffness substrate,and high stiffness hinge are developed.This high stiffness solar array mechanisms concept has been verified by ground tests and on-orbit flight of two GFDM-1 satellite solar arrays.In comparison with the traditional in-line rigid solar array of the same area,GFDM-1 satellite solar arrays achieved a 5-time increase of the first mode deployed frequency and an 7/8 reduction of deployment inertia.This new solar array concept can be used as a reference for design and development of other multi-panel in-parallel high stiffness solar array mechanisms.

关 键 词：高分多模卫星 太阳翼 展开机构 高刚度 在轨展开 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]